Aerospace Science and Technology最新文献_第8页

Simulation method for dynamic characteristics of rotor-support system subjected to environmental loads 受环境负荷影响的转子支撑系统动态特性模拟方法

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-06 DOI: 10.1016/j.ast.2024.109654

Fengguang Xiang, Xi Chen, Dezhi Yang, Guangming Ren, Xiaohua Gan

An improved finite element method was proposed to investigate the dynamic characteristics of rotor system with environmental loads (temperature and aerodynamic forces) in aeroengines. According to the axial temperature distribution within shaft elements, the polynomials were established for physical properties of material. The derivation for coefficient matrices under thermal loads, and the tensile stiffness matrix considering axial aerodynamic forces were completed, based on the Timoshenko beam theory. A high-pressure rotor was simulated with operating temperature

200 \sim 600^{\circ} C

, and the magnitude of aerodynamic force is

10^{5} N

. Furthermore, a squeezed film damper (SFD) was adopted to this rotor-support system, its steady responses were solved by the equivalent coefficient method, and the Newmark-HHT method was utilized to solve the transient responses. The results indicate that the first two critical speeds are reduced by 1.85 % and 2.07 %, which is mainly caused by thermal loads. The rising temperature leads to lower elastic modulus, higher Poisson's ratio and expansion ratio. With the amount of a mass unbalance being 500

g \cdot mm

located at the 1st-stage compressor disk (CD1): the 1st resonance peaks at CD1 and turbine disk (TD) increase by 4.56 % and 4.98 %, respectively, and the 2nd resonance peaks at CD1 and TD rise 5.88 % and 5.00 %, separately. Owing to SFD damping, the first two resonance peaks at CD1 and TD decrease by 69 % and 51 %, respectively. Compared to 40 °C, the first two resonance peaks at CD1 increase by 88 % and 55 % at the oil temperature 100 °C. The oil-film damping deteriorates significantly due to the lower oil viscosity in higher temperature. When operating near the first-order critical speed, the transient responses of rotor perform as simple harmonics, circular precession trajectory, dominant rotational frequency, and periodic motions. Overall, the dynamic characteristics of rotor-SFD-support systems exposed to environmental loads can be predicted by the proposed simulation method.

为研究航空发动机转子系统在环境负荷（温度和空气动力）作用下的动态特性，提出了一种改进的有限元方法。根据轴元件内的轴向温度分布，建立了材料物理性质的多项式。根据季莫申科梁理论，完成了热负荷下系数矩阵和考虑轴向空气动力的拉伸刚度矩阵的推导。模拟了工作温度为 200∼600∘C 的高压转子，空气动力大小为 105N。此外，该转子支撑系统采用了挤压薄膜阻尼器（SFD），其稳定响应采用等效系数法求解，瞬态响应采用 Newmark-HHT 法求解。结果表明，前两个临界转速分别降低了 1.85 % 和 2.07 %，这主要是由热负荷引起的。温度升高导致弹性模量降低，泊松比和膨胀比升高。当位于第一级压缩机盘（CD1）的质量不平衡量为 500 g-mm 时：CD1 和涡轮机盘（TD）的第一共振峰分别增加了 4.56 % 和 4.98 %，CD1 和 TD 的第二共振峰分别增加了 5.88 % 和 5.00 %。由于 SFD 的阻尼作用，CD1 和 TD 的前两个共振峰分别降低了 69 % 和 51 %。与 40 °C 相比，在油温 100 °C 时，CD1 处的前两个共振峰分别增加了 88 % 和 55 %。在较高温度下，由于油的粘度较低，油膜阻尼明显降低。在一阶临界转速附近运行时，转子的瞬态响应表现为简单谐波、圆前倾轨迹、主导旋转频率和周期性运动。总体而言，转子-SFD-支撑系统在环境负荷下的动态特性可以通过所提出的模拟方法进行预测。

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引用次数: 0

An improved analytical method for rarefied aerothermodynamics on a complex geometry in free-molecular flows 自由分子流中复杂几何体上稀薄空气热力学的改进分析方法

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-05 DOI: 10.1016/j.ast.2024.109644

Vignesh Ram Petha Sethuraman , Yosheph Yang , Hojun You , Jae Gang Kim

A numerical method for high altitude aerothermodynamic analysis code for Very Low Earth Orbit (VLEO) satellite and spacecraft, named as HACS, is presented in this article. HACS is a computational tool that addresses the challenges by integrating the free-molecular gas kinetic model with novel particle sampling method and robust particle tracing algorithm to predict the shadow region on surfaces. To ensure the reliability and accuracy of the HACS, a rigorous verification and validation process has been systematically conducted by comparing the aerothermodynamic properties of forces, moments, and heat flux with the direct simulation Monte-Carlo (DSMC) results. The HACS is applied to the realistic geometries of VLEO satellite, the Apollo re-entry module, and spacecraft including fin and wing shapes. Results demonstrate that HACS provides the aerothermodynamic properties within the time frame of 60 seconds for the complex geometries and the accuracy of the HACS is guaranteed above 120 km altitude. The maximum relative error of the aerothermodynamic properties is less than 5% compared to the DSMC results at the lowest altitude of about 120 km, and has smaller relative errors as the altitude increases.

本文介绍了一种用于甚低地球轨道（VLEO）卫星和航天器的高空空气热力学分析代码的数值方法，命名为 HACS。HACS 是一种计算工具，它将自由分子气体动力学模型与新颖的粒子采样方法和稳健的粒子追踪算法相结合，以预测表面阴影区域，从而应对各种挑战。为确保 HACS 的可靠性和准确性，通过比较力、力矩和热通量等空气热力学特性与直接模拟蒙特卡洛（DSMC）结果，系统地进行了严格的验证和确认过程。HACS 被应用于 VLEO 卫星、阿波罗返回舱以及包括鳍和翼形状在内的航天器的实际几何形状。结果表明，对于复杂的几何形状，HACS 可以在 60 秒的时间内提供空气热力学特性，并且在 120 千米高度以上可以保证 HACS 的精度。与 DSMC 的结果相比，在最低高度约 120 千米时，气动热力学特性的最大相对误差小于 5%，并且随着高度的增加，相对误差越来越小。

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引用次数: 0

Active fault-tolerant control with prescribed performance and reachability judgement for the altitude ground test facility 主动容错控制，为高空地面试验设施提供规定的性能和可达性判断

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-05 DOI: 10.1016/j.ast.2024.109653

Yuebin Lun , Honglun Wang , Jintao Hu , Guocheng Yan , Tiancai Wu , Bin Ren , Qiumeng Qian

This research proposes an active fault-tolerant control (AFTC) method based on reachability judgement with asymmetric appointed-time prescribed performance to ensure the safety of altitude ground test facility (AGTF) under potential valve actuator and sensor faults. Firstly, a long short-term memory (LSTM) neural network is employed for fault diagnosis. Given the unique characteristics of AGTF, the equivalent multiplicative fault is introduced to ensure the successful fitting of the fault diagnosis network. Then, a reachability judgement network based on the distance field on grids (DFOG) method is designed to assess the impact of faults on subsequent tasks of the system, thereby ensuring the safety of the AGTF. Subsequently, this study proposes an error transformation function of prescribed performance control (PPC) that ensures error convergence even in cases of asymmetric performance function. This enables the performance boundaries to be further reduced to improve the control performance of the system. Finally, experiments validate the effectiveness of the methods proposed in this manuscript.

本研究提出了一种基于可达性判断的主动容错控制（AFTC）方法，具有非对称指定时间规定性能，可确保高空地面试验设施（AGTF）在潜在阀门执行器和传感器故障下的安全性。首先，采用长短期记忆（LSTM）神经网络进行故障诊断。鉴于 AGTF 的特殊性，引入了等效乘法故障，以确保故障诊断网络的成功拟合。然后，设计了基于网格上距离场（DFOG）方法的可达性判断网络，以评估故障对系统后续任务的影响，从而确保 AGTF 的安全性。随后，本研究提出了规定性能控制（PPC）的误差变换函数，即使在性能函数不对称的情况下也能确保误差收敛。这使得性能边界可以进一步缩小，从而提高系统的控制性能。最后，实验验证了本手稿所提方法的有效性。

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引用次数: 0

Vibration characteristics of a pretwisted multi-blade-shaft system with blade stiffness mismatch 叶片刚度不匹配的预扭曲多叶片-轴系统的振动特性

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-04 DOI: 10.1016/j.ast.2024.109518

Ju Su , Yu Lin , Tian Yu Zhao

The substructure mode synthesis method is employed to establish a mathematical model in this paper. The main body is represented by shaft, while the branching components are represented by blades. By solving this model, accurate frequency results of the rotating blade-shaft system are obtained at a high computational speed that meets engineering requirements. The resulting mode diagram aligns with that of the finite element model. Utilizing this model, the stiffness detuning of the rotating blade shaft system is investigated through a combination of surrogate modeling and ant colony algorithm, leading to several significant findings. It is observed that an increase in the standard deviation of stiffness detuning amplifies the length of frequency interval while minimally affecting the frequency mean value. Moreover, an increase in average stiffness expands the interval length for system frequencies. Additionally, higher rotational speeds reduce the interval length for blade-dominant vibrations but extend it for shaft-dominant vibrations.

本文采用子结构模式合成法建立数学模型。轴代表主体，叶片代表分支部件。通过对该模型的求解，可获得叶片-轴旋转系统的精确频率结果，计算速度快，符合工程要求。所得到的模态图与有限元模型的模态图一致。利用该模型，结合代用建模和蚁群算法，对旋转叶片轴系统的刚度失谐进行了研究，得出了一些重要发现。研究发现，刚度失谐标准偏差的增加会放大频率间隔的长度，而对频率平均值的影响却很小。此外，平均刚度的增加会扩大系统频率的间隔长度。此外，转速越高，叶片主导振动的频率间隔长度越短，而轴主导振动的频率间隔长度则越长。

引用次数: 0

Aero-thermodynamic responses of a novel FGM sector disks using mathematical modeling and deep neural networks 利用数学建模和深度神经网络研究新型 FGM 扇形盘的空气热力学响应

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-04 DOI: 10.1016/j.ast.2024.109652

Shaoyong Han , Zhen Wang , Mohammed El-Meligy , Kashif Saleem

Composite sector disks have extensive applications in aerospace industries, particularly when exposed to challenging conditions such as supersonic airflow and thermal environments. These applications leverage the superior properties of composite materials, including high strength-to-weight ratios, enhanced durability, and excellent thermal resistance, to meet the stringent requirements of aerospace operations. Multi-directional functionally graded (MD-FG) materials due to high-temperature resistance and other amazing properties in each direction have gotten plenty of attention recently. So, in this research, a thermoelasticity solution has been presented to study fundamental frequency traits of an MD-FG sector disk in supersonic airflow via both mathematics simulation and deep neural networks technique. For obtaining exact displacement fields, along with defining the changes of transverse shear strains along the system's thickness, the refined zigzag hypothesis is utilized. For obtaining the temperature-dependent equations, heat conduction relation and thermal boundary conditions of the MD-FG structure are presented. A coupled quasi-3D new refined theory (Q3D-NRT) and generalized differential quadrature method (GDQM) are presented for obtaining and solving the partial differential equations in the time-displacement domain. After obtaining the mathematics results, appropriate datasets are made for testing, training, and validation of the deep neural networks technique. Finally, the results have shown that aerodynamic pressure, temperature changes, Mach number, free stream speed, and air yaw angle have a major role in the stability/instability analyses of the thermally affected MD-FG sector disk in supersonic airflow. As an amazing outcome, increasing the sector angle, FG indexes, and temperature change lead to the reduction of the critical Mach number, and aerodynamic pressure associated with the flutter phenomenon.

复合材料扇形盘在航空航天工业中有着广泛的应用，尤其是在面临超音速气流和热环境等挑战性条件时。这些应用充分利用了复合材料的优异性能，包括高强度重量比、更强的耐用性和出色的耐热性，以满足航空运营的严格要求。多向功能分级（MD-FG）材料由于在每个方向上都具有耐高温性和其他惊人的特性，最近受到了广泛关注。因此，本研究提出了一种热弹性解决方案，通过数学模拟和深度神经网络技术来研究 MD-FG 扇形盘在超音速气流中的基频特性。为了获得精确的位移场，同时定义横向剪切应变沿系统厚度的变化，利用了精炼之字形假说。为了获得与温度相关的方程，介绍了 MD-FG 结构的热传导关系和热边界条件。提出了一种准三维新精炼理论（Q3D-NRT）和广义微分正交法（GDQM）耦合方法，用于获取和求解时间-位移域中的偏微分方程。在获得数学结果后，制作了适当的数据集，用于测试、训练和验证深度神经网络技术。最后，研究结果表明，气动压力、温度变化、马赫数、自由流速度和空气偏航角对热影响 MD-FG 扇形盘在超音速气流中的稳定性/不稳定性分析具有重要作用。一个惊人的结果是，扇形角、FG 指数和温度变化的增加导致临界马赫数和与扑翼现象相关的空气动力压力的降低。

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引用次数: 0

Numerical study on flow control mechanism of endwall fence in a high-lift turbine rotor with open separation 开放式分离的高扬程涡轮转子端壁栅栏流动控制机制的数值研究

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-04 DOI: 10.1016/j.ast.2024.109651

Hang Yuan , Caiyan Chen , Hanliu Deng , Xiaoying Sheng , Xingen Lu , Yanfeng Zhang

The enhanced cross pressure gradient and the interference effect between secondary flow and separation bubble on the suction side make the refinement of flow organization in the endwall region a key role in improving the performance of low Reynolds number turbine stages. This influence is further amplified in high-lift turbines with open separation. The flow control method of applying endwall fence on a high-lift rotor of a low-speed turbine stage has been numerically studied. By analyzing the transformation of separation bubble on the suction surface and the development of vortices in the endwall region, the flow control mechanism of the endwall fence at low Reynolds numbers is presented. The influence of different fence design parameters on aerodynamic performance has been summarized. The research results indicate that the induced generation of fence vortex can effectively suppress passage vortex. After installing the fence, the intensification of blockage in the endwall region near the leading edge effectively delays the occurrence of laminar separation. Due to the introduction of additional endwall losses, the flow control effect of the fence mainly comes from the suppression of separation. The flow field in the endwall region and flow control effect are significantly affected by the pitchiwse position and height of the fence, while the width of the fence has a slight impact. The flow control effect can be more effectively achieved by designing the height variation of the fence reasonably. In addition, numerical results indicate that the optimized fence all exhibit good control effectiveness under different operating conditions.

交叉压力梯度的增强以及吸入侧二次流与分离气泡之间的干扰效应，使得端壁区域流动组织的细化成为提高低雷诺数涡轮级性能的关键因素。在采用开放式分离的高扬程涡轮机中，这种影响会进一步扩大。对在低速涡轮级的高扬程转子上应用端壁栅栏的流动控制方法进行了数值研究。通过分析分离气泡在吸气面上的变化和涡流在端壁区的发展，提出了端壁栅栏在低雷诺数下的流动控制机制。总结了不同栅栏设计参数对气动性能的影响。研究结果表明，栅栏涡流的诱导生成可以有效抑制通道涡流。安装栅栏后，前缘附近端壁区域阻塞的加剧有效延迟了层流分离的发生。由于引入了额外的端壁损失，栅栏的流动控制效果主要来自于对分离的抑制。内壁区域的流场和流量控制效果受栅栏的俯仰位置和高度影响较大，而栅栏的宽度影响较小。通过合理设计栅栏的高度变化，可以更有效地达到控流效果。此外，数值结果表明，优化后的栅栏在不同运行条件下均表现出良好的控制效果。

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引用次数: 0

Assessment of damage prediction models for composite laminates under single and repeated low-velocity impacts 复合材料层压板在单次和多次低速冲击下的损伤预测模型评估

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-04 DOI: 10.1016/j.ast.2024.109633

Fengzhong Li, Shijie Jin, Weiran Li, Zhongbing Luo

The aim is to explore the influence of damage initiation criteria and evolution methods on the damage prediction for composite laminates under single and repeated low-velocity impacts. A 3D finite element model is established to analyze the impact behavior of laminate, and a damage analysis process including the initiation determination, progressive evolution, and constitutive relationship is designed. Hashin criterion based on tensile strain for matrix is modified by an empirical assumption method. Besides, the quantitative evolution of damage area during impact is studied, which provides a new perspective for elucidating the damage mechanism. The numerical model is first validated against the available experimental data. The influence of initiation criteria and evolution methods on damage prediction is then performed in two-phase research. The first phase discusses the prediction capabilities of different combinations under single impact. In the second phase, a method for removing residual vibrations under repeated impacts is proposed. The differences caused by the removal and non-removal of residual vibrations are analyzed, and the sensitivity of these differences to various combinations is discussed. Results show that the numerical prediction agrees well with the experiment in dynamic mechanical response curve. Combining Hashin-Strain criterion with linear equivalent strain method and Puck criterion with exponential equivalent displacement method yields optimal results. Moreover, the sensitivity to differences caused by the residual vibrations effects is related to the initiation criterion, and the evolution method.

目的是探讨复合材料层压板在单次和多次低速冲击下的损伤起始标准和演化方法对损伤预测的影响。建立了一个三维有限元模型来分析层压板的冲击行为，并设计了一个包括起始判定、渐进演化和构成关系在内的损伤分析流程。基于基体拉伸应变的 Hashin 准则通过经验假设法进行了修正。此外，还研究了冲击过程中损伤面积的定量演变，为阐明损伤机理提供了新的视角。首先根据现有的实验数据对数值模型进行了验证。然后分两个阶段研究了起始标准和演化方法对损伤预测的影响。第一阶段讨论了单一冲击下不同组合的预测能力。在第二阶段，提出了在重复冲击下消除残余振动的方法。分析了消除和不消除残余振动造成的差异，并讨论了这些差异对不同组合的敏感性。结果表明，在动态机械响应曲线方面，数值预测与实验结果吻合良好。将 Hashin-Strain 准则与线性等效应变法相结合，以及将 Puck 准则与指数等效位移法相结合，可获得最佳结果。此外，残余振动效应引起的差异敏感性与起始准则和演化方法有关。

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引用次数: 0

Multi-objective optimization of airfoils with integral tubular high-pressure tanks for hydrogen storage 用于储氢的带整体管状高压罐机翼的多目标优化

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-03 DOI: 10.1016/j.ast.2024.109647

Florian Dexl, Andreas Hauffe, Johannes Markmiller

Reducing the environmental impact of air transport is one of today's most important challenges in aviation industry and research. A promising key enabler is the use of hydrogen as an alternative to fossil fuels. The development of hydrogen-powered aircraft poses new engineering challenges due to its low volumetric energy density requiring high-pressure or cryogenic storage. If the volume in the wing shall be further used for storing hydrogen under high pressure, new demands arise to airfoil design. The present work focuses on this issue by presenting a multi-objective optimization approach aiming for airfoils with both low drag and high volume for internal tubular high-pressure tanks. This allows to directly address the new design objective and to find novel airfoil shapes providing the best compromise between aerodynamic efficiency and high storage volume for pressurized hydrogen. The resulting optimization problem is solved using Evolutionary Algorithms. For an efficient aerodynamic evaluation, the open source viscous-inviscid panel method XFOIL is used. An application example, based on the flight conditions of a general aviation aircraft, demonstrates the applicability of the method. Comparisons of the resulting aerodynamic characteristics obtained by XFOIL with RANS simulations confirm the feasibility of the results.

减少航空运输对环境的影响是当今航空业和研究领域最重要的挑战之一。氢气作为化石燃料的替代品是一个前景广阔的关键推动因素。由于氢气的体积能量密度低，需要高压或低温储存，这给氢动力飞机的开发带来了新的工程挑战。如果进一步利用机翼的体积在高压下储存氢气，就会对机翼设计提出新的要求。本研究针对这一问题，提出了一种多目标优化方法，旨在为内部管状高压储氢罐设计低阻力和大容积的机翼。这样就能直接解决新的设计目标，并找到新型机翼形状，在加压氢气的气动效率和高存储容量之间实现最佳折衷。由此产生的优化问题使用进化算法进行求解。为了进行有效的气动评估，使用了开源的粘性-内粘性面板方法 XFOIL。一个基于通用航空飞机飞行条件的应用实例证明了该方法的适用性。将 XFOIL 与 RANS 模拟得出的气动特性进行比较，证实了结果的可行性。

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引用次数: 0

Dynamic event-triggered neuroadaptive fault-tolerant control of quadrotor UAV with a novel cosine kernel 利用新型余弦核对四旋翼无人机进行动态事件触发神经自适应容错控制

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-02 DOI: 10.1016/j.ast.2024.109643

Nabarun Sarkar , Alok Kanti Deb

The fault-tolerant control (FTC) for trajectory tracking of a quadrotor unmanned aerial vehicle (UAV) has attracted researchers. The non-linear model of the UAV, coupled with model uncertainties, external disturbances, and actuator failures, requires the function approximation of the lumped non-linearity for controller design. One of the most efficient ways to approximate non-linearity is using radial basis function neural networks (RBFNNs). To date, RBFNNs have been formulated, trained, and used directly for function approximation, which requires considerable computation to derive the control laws. The proposed control and parameter estimation laws approximate the non-linearity by using RBFNNs indirectly. The proposed laws with virtual parameter estimation do not require the actual formulation of RBFNNs and their weights, thus saving on computational resources. For kernel optimization, the Gaussian kernels with exponential terms in RBFNNs are replaced by cosine kernels with algebraic terms, which shows faster convergence as per simulation results. To save on communication bandwidth, static event-triggering communication mechanisms (SECM) and dynamic event-triggering mechanisms (DECM) have been proposed. As DECM works on dynamically changing variables, it saves more communication bandwidth, as tested in simulation. Lyapunov stability analysis proves that errors are uniformly ultimately bounded (UUB). The performance of the proposed algorithm has been tested through numerical simulations, which show superior performance when compared with similar studies. The proposed algorithm has been validated in a real-time Gazebo simulator.

用于四旋翼无人飞行器（UAV）轨迹跟踪的容错控制（FTC）吸引了众多研究人员。无人飞行器的非线性模型，加上模型不确定性、外部干扰和致动器故障，需要对控制器设计中的集合非线性进行函数逼近。逼近非线性的最有效方法之一是使用径向基函数神经网络（RBFNN）。迄今为止，RBFNNs 已被制定、训练和直接用于函数逼近，这需要大量计算才能得出控制法则。拟议的控制和参数估计法则通过使用 RBFNNs 间接逼近非线性。拟议的虚拟参数估计法则不需要实际制定 RBFNN 及其权重，从而节省了计算资源。在内核优化方面，RBFNN 中带有指数项的高斯内核被带有代数项的余弦内核所取代，模拟结果表明收敛速度更快。为了节省通信带宽，有人提出了静态事件触发通信机制（SECM）和动态事件触发机制（DECM）。由于 DECM 是针对动态变化的变量工作的，因此经仿真测试，它能节省更多的通信带宽。李亚普诺夫稳定性分析证明，误差是均匀最终有界的（UUB）。通过数值模拟测试了所提算法的性能，结果表明与同类研究相比，该算法性能更优。拟议算法已在实时 Gazebo 仿真器中得到验证。

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引用次数: 0

A maneuvering strategy based on motion camouflage in three-player differential game 三人差分游戏中基于运动伪装的机动策略

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2024-10-02 DOI: 10.1016/j.ast.2024.109642

Jianqing Li , Qiancheng Zhao , Chaoyong Li , Zhaohui Song

In this paper, we consider a three-player differential game in which the defender provides coverage for the evader by maneuvering toward the line of sight between the pursuer and the evader. The TAD game is divided into two pursuit-evasion games to obtain the saddle point strategy for each player. Different from the general solution, the defender uses motion camouflage conditions as its payoff function and gives the real-time maneuvering strategy. This approach ensures that the constraint in the gaming process is met by providing the saddle point solution for each time interval. Additionally, interception strategies are created for each player to get the required heading angle. These strategies and game dynamics can be predicted by examining the current state of the game. Consequently, we establish the advantage region for the pursuer and the defender based on these predictions. Based on the given initial conditions, the advantage region for the defender is presented in its initial velocity vector. Finally, the simulations validate the effectiveness of the proposed strategy and the capture region analysis.

在本文中，我们考虑了一种三人差分博弈，其中防守方通过向追逐者和规避者之间的视线方向机动来为规避者提供掩护。TAD 博弈被分为两个追逐-规避博弈，从而得到每个玩家的鞍点策略。与一般解法不同的是，防御方使用运动伪装条件作为其报酬函数，并给出实时机动策略。这种方法通过提供每个时间间隔的鞍点解来确保满足博弈过程中的约束条件。此外，还为每个玩家创建了拦截策略，以获得所需的航向角。这些策略和博弈动态可通过检查博弈的当前状态进行预测。因此，我们会根据这些预测为追击方和防守方建立优势区域。根据给定的初始条件，防御方的优势区域将以其初始速度矢量呈现。最后，模拟验证了建议策略和捕获区域分析的有效性。

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引用次数: 0